EP1229146A2 - Oxidation resistant coatings for niobium-based silicide composites - Google Patents
Oxidation resistant coatings for niobium-based silicide composites Download PDFInfo
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- EP1229146A2 EP1229146A2 EP02250499A EP02250499A EP1229146A2 EP 1229146 A2 EP1229146 A2 EP 1229146A2 EP 02250499 A EP02250499 A EP 02250499A EP 02250499 A EP02250499 A EP 02250499A EP 1229146 A2 EP1229146 A2 EP 1229146A2
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- EP
- European Patent Office
- Prior art keywords
- niobium
- resistant coating
- environmentally resistant
- atomic percent
- refractory metal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 239000010955 niobium Substances 0.000 title claims abstract description 209
- 238000000576 coating method Methods 0.000 title claims abstract description 145
- 229910052758 niobium Inorganic materials 0.000 title claims abstract description 126
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 title claims abstract description 126
- 230000003647 oxidation Effects 0.000 title abstract description 23
- 238000007254 oxidation reaction Methods 0.000 title abstract description 23
- FVBUAEGBCNSCDD-UHFFFAOYSA-N silicide(4-) Chemical class [Si-4] FVBUAEGBCNSCDD-UHFFFAOYSA-N 0.000 title 1
- 239000011248 coating agent Substances 0.000 claims abstract description 140
- 239000003870 refractory metal Substances 0.000 claims abstract description 73
- 239000002131 composite material Substances 0.000 claims abstract description 71
- 239000010936 titanium Substances 0.000 claims abstract description 71
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 61
- 239000010703 silicon Substances 0.000 claims abstract description 61
- 239000011651 chromium Substances 0.000 claims abstract description 59
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 58
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims abstract description 58
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 58
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 57
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 57
- 239000000758 substrate Substances 0.000 claims abstract description 52
- 238000000034 method Methods 0.000 claims abstract description 25
- 239000012720 thermal barrier coating Substances 0.000 claims abstract description 25
- 238000000151 deposition Methods 0.000 claims description 24
- 229910052735 hafnium Inorganic materials 0.000 claims description 23
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 claims description 23
- 239000002002 slurry Substances 0.000 claims description 14
- 239000000463 material Substances 0.000 claims description 12
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 claims description 10
- 239000011230 binding agent Substances 0.000 claims description 4
- 238000005229 chemical vapour deposition Methods 0.000 claims description 4
- 230000008021 deposition Effects 0.000 claims description 4
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 claims description 4
- 238000007598 dipping method Methods 0.000 claims description 4
- 150000002500 ions Chemical class 0.000 claims description 4
- 229910052863 mullite Inorganic materials 0.000 claims description 4
- 238000005240 physical vapour deposition Methods 0.000 claims description 4
- 238000010290 vacuum plasma spraying Methods 0.000 claims description 4
- 229910052845 zircon Inorganic materials 0.000 claims description 4
- GFQYVLUOOAAOGM-UHFFFAOYSA-N zirconium(iv) silicate Chemical compound [Zr+4].[O-][Si]([O-])([O-])[O-] GFQYVLUOOAAOGM-UHFFFAOYSA-N 0.000 claims description 4
- 239000000446 fuel Substances 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 238000005507 spraying Methods 0.000 claims description 3
- 229910002076 stabilized zirconia Inorganic materials 0.000 claims description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 26
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 14
- 229910052732 germanium Inorganic materials 0.000 description 14
- GNPVGFCGXDBREM-UHFFFAOYSA-N germanium atom Chemical compound [Ge] GNPVGFCGXDBREM-UHFFFAOYSA-N 0.000 description 14
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 13
- 229910052796 boron Inorganic materials 0.000 description 13
- 229910052742 iron Inorganic materials 0.000 description 13
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 description 10
- 229910000601 superalloy Inorganic materials 0.000 description 10
- 229910052715 tantalum Inorganic materials 0.000 description 10
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 10
- 229910052718 tin Inorganic materials 0.000 description 10
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 9
- 229910052750 molybdenum Inorganic materials 0.000 description 9
- 239000011733 molybdenum Substances 0.000 description 9
- 229910052782 aluminium Inorganic materials 0.000 description 8
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 8
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 7
- 229910052721 tungsten Inorganic materials 0.000 description 7
- 239000010937 tungsten Substances 0.000 description 7
- 229910001233 yttria-stabilized zirconia Inorganic materials 0.000 description 4
- 230000008018 melting Effects 0.000 description 3
- 238000002844 melting Methods 0.000 description 3
- 239000011819 refractory material Substances 0.000 description 3
- 230000004888 barrier function Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- 238000001878 scanning electron micrograph Methods 0.000 description 2
- 229910021332 silicide Inorganic materials 0.000 description 2
- 229910052684 Cerium Inorganic materials 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- GWXLDORMOJMVQZ-UHFFFAOYSA-N cerium Chemical compound [Ce] GWXLDORMOJMVQZ-UHFFFAOYSA-N 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000010285 flame spraying Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 238000007750 plasma spraying Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000004626 scanning electron microscopy Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000005382 thermal cycling Methods 0.000 description 1
- 229910052727 yttrium Inorganic materials 0.000 description 1
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
- C23C10/18—Solid state diffusion of only metal elements or silicon into metallic material surfaces using liquids, e.g. salt baths, liquid suspensions
- C23C10/26—Solid state diffusion of only metal elements or silicon into metallic material surfaces using liquids, e.g. salt baths, liquid suspensions more than one element being diffused
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
- C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
- C23C10/60—After-treatment
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
- Y10T428/12611—Oxide-containing component
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
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- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
- Y10T428/12611—Oxide-containing component
- Y10T428/12618—Plural oxides
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12674—Ge- or Si-base component
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
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- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12771—Transition metal-base component
- Y10T428/12806—Refractory [Group IVB, VB, or VIB] metal-base component
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12771—Transition metal-base component
- Y10T428/12806—Refractory [Group IVB, VB, or VIB] metal-base component
- Y10T428/12819—Group VB metal-base component
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/26—Web or sheet containing structurally defined element or component, the element or component having a specified physical dimension
- Y10T428/263—Coating layer not in excess of 5 mils thick or equivalent
- Y10T428/264—Up to 3 mils
- Y10T428/265—1 mil or less
Definitions
- the present invention relates to turbine systems. More particularly, the invention relates to components of such turbine systems. Still more particularly, the invention relates to turbine components formed from a niobium-based refractory metal intermetallic composite. Finally, the invention relates to environmentally resistant coatings for such turbine components.
- Turbine systems such as, but not limited to, aeronautical turbines, land-based, turbines, marine-based turbines, and the like, and their components (hereinafter referred to as "turbine components") have typically been formed from nickel (Ni) based materials, which are often referred to as Ni-based superalloys.
- Turbine components formed from these Ni-based superalloys exhibit desirable chemical and physical properties under the high temperature, high stress, and high-pressure conditions generally encountered during turbine operation.
- the highest surface temperatures of state-of-the-art jet engine turbine airfoils reach as high as about 2100°F (about 1150°C), or about 85% of the melting temperature (T m ) of most of the Ni-based superalloys.
- Ni-based superalloys have provided the desired level of performance for turbine system applications, causing the development of such Ni-based superalloys to be widely explored.
- the field has matured and few significant improvements have been realized in this area in recent years.
- efforts have been made to develop alternative turbine component materials.
- Nb-based RMICs niobium (Nb) based refractory metal intermetallic composites
- Most Nb-based RMICs have melting temperatures of greater than about 3100°F (about 1700°C). If Nb-based RMICs can be used at about 80% of their melting temperatures, they will have potential use in applications in which the temperature exceeds the current service limit of Ni-based superalloys.
- Nb-based RMICs comprising niobium (Nb), silicon (Si), titanium (Ti), hafnium (Hf), chromium (Cr), and aluminum (Al) are among the materials that have been proposed for turbine component applications in which Ni-based superalloys are presently used. These Nb-based RMICs exhibit a high temperature capability which exceeds that of the Ni-based superalloys that are currently used in such applications. Exemplary Nb-based RMICs are described by Jackson and Bewlay (U.S. Patents 5,932,033 and 5,942,055), and more recently by Jackson, Bewlay, and Zhao in U.S.
- Nb-based RMICs show potential for use as next-generation turbine components having service temperatures that are significantly greater than those of current Ni-based superalloy components, oxidation of such turbine components remains a concern.
- temperatures in the range between about 2000°F and about 2500°F between about 1090°C and about 1370°C
- refractory materials can undergo rapid oxidation.
- a slow-growing oxide scale can form on Nb-based RMIC's at this temperature, it is typically not a protective oxide scale.
- Another type of oxidation known as 'pesting' occurs at intermediate temperatures (e.g., between about1400°F and about 1800°F).
- Pesting is a phenomenon that is characterized by the disintegration of a material into pieces or powders after exposure to air at intermediate temperatures.
- Refractory metals, particularly molybdenum exhibit poor resistance to pesting oxidation.
- Nb-based RMICs While significant progress has been made in improving the oxidation performance of Nb-based RMICs, it is desirable to provide coatings for turbine components fabricated from these materials in order to ensure long lifetimes at service temperatures of 2000°F to 2500°F. Therefore, what is needed is a turbine system having Nb-based RMIC components having coatings that will provide increased resistance of the components to oxidation at temperatures in the range between about 2000°F and about 2500°F and increased resistance to pesting at temperatures between about 1400°F an about 1800°F. What is also needed is an environmentally resistant coating for Nb-based RMICs, which will enhance oxidation resistance at high temperatures and pesting resistance at intermediate temperatures.
- the present invention meets these needs and others by providing a turbine system that includes Nb-based RMIC components having coatings that increase oxidation resistance at high temperatures and resistance to pesting at intermediate temperatures.
- the present invention also provides an environmentally resistant coating for Nb-based RMICs that exhibit improved oxidation resistance at high temperatures and resistance to pesting at intermediate temperatures.
- methods for making a coated Nb-based RMIC turbine component and coating a Nb-based RMIC are also disclosed.
- one aspect of the present invention is to provide a turbine system having at least one turbine component.
- the turbine component comprises: a niobium-based refractory metal intermetallic composite (Nb-based RMIC) comprising titanium, hafnium, silicon, chromium, and niobium; and an environmentally resistant coating disposed on a surface of the niobium-based refractory metal intermetallic composite, the environmentally resistant coating comprising silicon, titanium, chromium, and niobium.
- Nb-based RMIC niobium-based refractory metal intermetallic composite
- a second aspect of the invention is to provide an environmentally resistant coating for a niobium-based refractory metal intermetallic composite (Nb-based RMIC) substrate.
- the environmentally resistant coating comprises between about 43 and 67 atomic percent silicon; between about 2 and about 25 atomic percent titanium; between about 1 and about 25 atomic percent chromium; and a balance of niobium.
- a third aspect of the invention is to provide a turbine system having at least one turbine component.
- the turbine component comprises: a niobium-based refractory metal intermetallic composite (Nb-based RMIC), said niobium-based refractory metal intermetallic composite comprising titanium, hafnium, silicon, chromium, and a balance of niobium; an environmentally resistant coating disposed on a surface of the niobium-based refractory metal intermetallic composite substrate; and a thermal barrier coating disposed on an outer surface of the environmentally resistant coating.
- the environmentally resistant coating comprises between about 43 and 67 atomic percent silicon; between about 2 and about 25 atomic percent titanium; between about 1 and about 25 atomic percent chromium; and a balance of niobium.
- a fourth aspect of the invention is to provide a method of making a turbine component comprising a niobium-based refractory metal intermetallic composite (Nb-based RMIC) and having an environmentally resistant coating disposed on the surface of the component,
- the environmentally resistant coating comprises silicon, titanium, chromium, and niobium.
- the method comprises the steps of providing a niobium-based refractory metal intermetallic composite substrate formed into the turbine component and depositing the environmentally resistant coating onto the surface of the component.
- a fifth aspect of the present invention is to provide a method of coating a niobium-based refractory metal intermetallic composite (Nb-based RMIC) substrate with an environmentally resistant coating.
- the environmentally resistant coating comprises silicon, titanium, chromium, and a balance of niobium.
- the method comprises the steps of providing a niobium-based refractory metal intermetallic composite substrate and depositing the environmentally resistant coating onto the surface of the niobium-based refractory metal intermetallic composite substrate.
- FIG. 1 is a schematic diagram of a turbine system 10 of the present invention.
- the turbine system 10 may either be an aircraft engine; a land-based turbine system, such as those widely used for power generation; or a marine-based turbine.
- the turbine system 10 of the present invention comprises a number of turbine components 11 that are subject to temperatures of about 2100°F (about 1150°C) or greater during normal operation.
- These turbine components 11 include, but are not limited to: rotating blades 12, vanes 16, shrouds 18, nozzles 20, combustors 24, and the like.
- Such turbine components 11 are formed from niobium-based refractory metal intermetallic composites (hereinafter referred to as "Nb-based RMICs”) and have service temperatures that are either at the limit of or exceed those of similar components formed from nickel-based superalloys that are currently in use.
- Nb-based RMICs niobium-based refractory metal intermetallic composites
- the Nb-based RMICs that are used to form the turbine components 11 of the turbine system 10 comprise titanium, hafnium, silicon, chromium, and niobium.
- the Nb-based RMICs preferably each comprise between about 19 atomic percent and about 24 atomic percent titanium; between about 1 atomic percent and about 5 atomic percent hafnium; between about 11 and about 22 atomic percent silicon; between about 5 and about 14 atomic percent chromium; and a balance of niobium.
- the Nb-based RMICs each comprise between about 19 and about 24 atomic percent titanium; between about 1 and about 5 atomic percent hafnium; up to about 7 atomic percent tantalum; between about 11 and about 22 atomic percent silicon; up to about 6 atomic percent germanium; up to about 12 atomic percent boron; between about 5 and about 14 atomic percent chromium; up to about 4 atomic percent iron; up to about 4 atomic percent aluminum; up to about 3 atomic percent tin; up to about 3 atomic percent tungsten; up to about 3 atomic percent molybdenum; and a balance of niobium.
- silicon, germanium, and boron together comprise between about 11 and about 24 atomic percent of the Nb-based RMIC
- iron and chromium together comprise between about 5 and about 14 atomic percent of the Nb-based RMIC
- a ratio of a sum of atomic percentages of niobium and tantalum present in the Nb-based RMIC to a sum of atomic percentages of titanium and hafnium in the Nb-based RMIC has a value of between about 1.4 and about 2.2; i.e., 1.4 ⁇ (Nb+Ta):(Ti+Hf) ⁇ 2.2.
- oxidation of the turbine components 10 formed from Nb-based RMICs is a concern, as such materials can undergo rapid oxidation at temperatures in the range between about 2000°F and about 2500°F (between about 1090°C and about 1370°C.
- the slow-growing oxide scale that usually forms on Nb-based RMIC's at these temperatures is typically not a protective oxide scale.
- another type of oxidation known as 'pesting,' occurs at intermediate temperatures (e.g., between about1400°F an about 1800°F).
- Pesting is a phenomenon that is characterized by the disintegration of a material into pieces or powders after exposure at intermediate temperatures. Refractory metals, particularly molybdenum, exhibit poor resistance to pesting oxidation.
- the present invention includes an environmentally resistant coating 34 disposed on a surface 33 of the Nb-based RMIC substrate 32 to form a coated Nb-based RMIC article 30, such as a coated turbine component, as shown in Figure 2.
- the environmentally resistant coating 34 has a thickness of between about 10 microns and about 200 microns and comprises silicon, titanium, chromium, and niobium. It is desirable that the environmentally resistant coating 34 comprise between about 43 and 67 atomic percent silicon; between about 2 and about 25 atomic percent titanium; between about 1 and about 25 atomic percent chromium; and a balance of niobium.
- the environmentally resistant coating 34 may further comprise at least one metal selected from the group consisting of boron, iron, and tin, wherein the total amount of these elements comprises less than about 5 atomic percent of the environmentally resistant coating.
- the environmentally resistant coating 34 may further comprise up to about 20 atomic percent germanium, where germanium replaces silicon.
- the environmentally resistant coating 34 may also include up to about 3 atomic percent of at least one element selected from the group consisting of hafnium, tantalum, aluminum, tungsten, and molybdenum.
- the environmentally resistant coating 34 preferably comprises between about 50 and about 67 atomic percent silicon, between about 8 and about 16 atomic percent titanium, between about 4 and about 12 atomic percent chromium, and a balance of niobium. Most preferably, the environmentally resistant coating 34 comprises about 66 atomic percent silicon, about 10 atomic percent titanium, about 5 atomic percent chromium, and a balance of niobium.
- the phase Nb 1-x-y Ti x Cr y Si 2 phase in which 1 > (x+y) ⁇ 0, comprises at least about 50 volume percent of the environmentally resistant coating.
- the phase Nb 1-x-y Ti x Cr y Si 2 may be concentrated in an outer region 36 adjacent to the outer surface 40 of the environmentally resistant coating 34.
- Other phases such as a Ti 5-z Nb z Si 4 phase, and a Ti 5-w Nb w Si 3 phase, where 5 > z, w ⁇ 0, may also be present in the environmentally resistant coating 34.
- These phases may also contain small amounts of chromium and hafnium, and may be concentrated in an interfacial zone 38 adjacent to the interface 39 between the environmentally resistant coating 34 and of the Nb-based RMIC substrate 32.
- the environmentally resistant coating 34 may be applied to a Nb-based RMIC substrate 32, such as a turbine component 11, by one of a number of deposition techniques.
- One such technique is to dip the Nb-based RMIC substrate 32 into a slurry comprising a viscous binder and containing silicon, chromium, and titanium. After dipping, the Nb-based RMIC substrate 32 is then heat treated at a temperature of at least about 1200°C, preferably for at least about one hour, to form the environmentally resistant coating 34. During the heat treatment at 1200°C, the slurry reacts with niobium in the Nb-based RMIC substrate 32 to form the environmentally resistant layer of the present invention.
- An additional heat treatment at 1600°C for 10 hours may be used to consolidate the environmentally resistant coating 34.
- Other methods including ion plasma deposition, vacuum plasma spraying, high velocity oxy-flame spraying, physical vapor deposition, chemical vapor deposition, and combinations thereof, can be used to deposit silicon, chromium, titanium, and niobium on the Nb-based RMIC substrate 32.
- the environmentally resistant coating 34 is then formed by heat treating the Nb-based RMIC substrate 32 at a temperature of at least about 1200°C, preferably for at least about one hour.
- a thermal barrier coating 42 may be applied in addition to the environmentally resistant coating 34 to provide a thermal barrier coated Nb-based RMIC article 50, such as a coated turbine component, as shown in Figure 3.
- the thermal barrier coating 42 is deposited on the outer surface 40 of the environmentally resistant coating 34.
- the thermal barrier coating 42 has a thickness of between about 50 microns and about 400 microns, and may comprise: zirconia; zirconia stabilized by the addition of other metals, such as yttrium, magnesium, cerium, and the like; zircon; mullite; combinations thereof; or other refractory materials having similar properties.
- the thermal barrier coated turbine component 50 may installed in the turbine system 10.
- Nb-based RMIC test buttons were coated with the environmentally resistant coating of the present invention.
- a thermal barrier coating of yttria-stabilized zirconia (YSZ) was deposited on top of the environmentally resistant coating using an air plasma spraying method.
- a representative microstructure of a test button 62 coated with the environmentally resistant coating 34 of the present invention and the YSZ thermal barrier coating 42 is shown in Figure 4.
- the environmentally resistant coating 34 shown in Figure 4 has a composition of about 66 atomic percent silicon, about 10 atomic percent titanium, about 5 atomic percent chromium, and about 19 atomic percent niobium.
- the phase Nb 1-x-y Ti x Cr y Si 2 is concentrated in an outer region 36 adjacent to the outer surface 40 of the environmentally resistant coating 34.
- the interfacial zone 38 of the environmentally resistant coating 34 adjacent to the substrate test button 62 contains a Ti 5-x Nb x Si 4 phase and a Ti 5-x Nb x Si 3 phase.
- the interaction zone 38 has a composition of about 44 atomic percent silicon, about 19 atomic percent titanium, about 5 atomic percent chromium, about 1 atomic percent hafnium, and about 31 atomic percent niobium. Due to the brittle nature of the Nb 1-x-y Ti x Cr y Si 2 phase and the difference in coefficients of thermal expansion (CTE) between the different phases, cracks 54 have formed in the environmentally resistant coating. These cracks 54 are self-healing; i.e., they do not propagate further with additional high temperature exposure or thermal cycling.
- the Nb-based RMIC test buttons 62 coated with the environmentally resistant coating 34 of the present invention and the YSZ thermal barrier coating 42 were subjected to furnace cycle tests (FCT) to 1600°F, 2400°F, and 2500°F.
- FCT furnace cycle tests
- the coated Nb-based RMIC test buttons were heated to the high temperature for 1 hour in air and then removed from the furnace and cooled for 10 minutes with blowing air. The specimens were then re-loaded into the high temperature furnace. These tests were repeated for 100 times, or cycles, for each test temperature.
- a post-FCT examination of the coated Nb-based RMIC test buttons was carried out using scanning electron microscopy (SEM).
- FIG. 5 A representative SEM image of a cross section of a coated Nb-based RMIC test button that had been subjected to a furnace cycle test to 2500°F for 100 cycles is shown in Figure 5.
- the thermal barrier coating 42 and environmentally resistant coating 34 remained intact and still adhered to the Nb-based RMIC test button 62 substrate.
- no internal oxidation of the Nb-based RMIC test button 62 substrates was observed during the SEM examination.
- no pesting of the Nb-based RMIC test button 62 substrates was observed at any of the test temperatures.
- the furnace cycle tests thus show that the susceptibility of Nb-based RMICS to both high temperature oxidation and pesting at intermediate temperatures is significantly reduced by the presence of the environmentally resistant coating of the present invention and a thermal barrier coating.
- the method of depositing the environmentally resistant coating may include any combination of the various methods described herein.
- the thermal barrier coating may comprise other refractory materials other than those described herein.
- Nb-based RMICs having the environmentally resistant coating may find use other applications in which oxidation resistance at high temperature materials is a desired property.
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Abstract
Description
- The present invention relates to turbine systems. More particularly, the invention relates to components of such turbine systems. Still more particularly, the invention relates to turbine components formed from a niobium-based refractory metal intermetallic composite. Finally, the invention relates to environmentally resistant coatings for such turbine components.
- Turbine systems, such as, but not limited to, aeronautical turbines, land-based, turbines, marine-based turbines, and the like, and their components (hereinafter referred to as "turbine components") have typically been formed from nickel (Ni) based materials, which are often referred to as Ni-based superalloys. Turbine components formed from these Ni-based superalloys exhibit desirable chemical and physical properties under the high temperature, high stress, and high-pressure conditions generally encountered during turbine operation. For example, the highest surface temperatures of state-of-the-art jet engine turbine airfoils reach as high as about 2100°F (about 1150°C), or about 85% of the melting temperature (Tm) of most of the Ni-based superalloys.
- To date, the Ni-based superalloys have provided the desired level of performance for turbine system applications, causing the development of such Ni-based superalloys to be widely explored. As a result of such extensive study, the field has matured and few significant improvements have been realized in this area in recent years. In the meantime, efforts have been made to develop alternative turbine component materials.
- These alternative materials include niobium (Nb) based refractory metal intermetallic composites (hereinafter referred to as "Nb-based RMICs"). Most Nb-based RMICs have melting temperatures of greater than about 3100°F (about 1700°C). If Nb-based RMICs can be used at about 80% of their melting temperatures, they will have potential use in applications in which the temperature exceeds the current service limit of Ni-based superalloys.
- Nb-based RMICs comprising niobium (Nb), silicon (Si), titanium (Ti), hafnium (Hf), chromium (Cr), and aluminum (Al) are among the materials that have been proposed for turbine component applications in which Ni-based superalloys are presently used. These Nb-based RMICs exhibit a high temperature capability which exceeds that of the Ni-based superalloys that are currently used in such applications. Exemplary Nb-based RMICs are described by Jackson and Bewlay (U.S. Patents 5,932,033 and 5,942,055), and more recently by Jackson, Bewlay, and Zhao in U.S. Patent applications titled "Niobium-Silicide Based Composites Resistant to High Temperature Oxidation" (Serial No. ; filed December 13, 2000) and "Niobium-Silicide Based Composites Resistant to Low Temperature Pesting" (Serial No. 09/735,769; filed December 13, 2000).
- Although the Nb-based RMICs show potential for use as next-generation turbine components having service temperatures that are significantly greater than those of current Ni-based superalloy components, oxidation of such turbine components remains a concern. At temperatures in the range between about 2000°F and about 2500°F (between about 1090°C and about 1370°C), refractory materials can undergo rapid oxidation. While a slow-growing oxide scale can form on Nb-based RMIC's at this temperature, it is typically not a protective oxide scale. Another type of oxidation known as 'pesting' occurs at intermediate temperatures (e.g., between about1400°F and about 1800°F). Pesting is a phenomenon that is characterized by the disintegration of a material into pieces or powders after exposure to air at intermediate temperatures. Refractory metals, particularly molybdenum, exhibit poor resistance to pesting oxidation.
- While significant progress has been made in improving the oxidation performance of Nb-based RMICs, it is desirable to provide coatings for turbine components fabricated from these materials in order to ensure long lifetimes at service temperatures of 2000°F to 2500°F. Therefore, what is needed is a turbine system having Nb-based RMIC components having coatings that will provide increased resistance of the components to oxidation at temperatures in the range between about 2000°F and about 2500°F and increased resistance to pesting at temperatures between about 1400°F an about 1800°F. What is also needed is an environmentally resistant coating for Nb-based RMICs, which will enhance oxidation resistance at high temperatures and pesting resistance at intermediate temperatures.
- The present invention meets these needs and others by providing a turbine system that includes Nb-based RMIC components having coatings that increase oxidation resistance at high temperatures and resistance to pesting at intermediate temperatures. The present invention also provides an environmentally resistant coating for Nb-based RMICs that exhibit improved oxidation resistance at high temperatures and resistance to pesting at intermediate temperatures. In addition, methods for making a coated Nb-based RMIC turbine component and coating a Nb-based RMIC are also disclosed.
- Accordingly, one aspect of the present invention is to provide a turbine system having at least one turbine component. The turbine component comprises: a niobium-based refractory metal intermetallic composite (Nb-based RMIC) comprising titanium, hafnium, silicon, chromium, and niobium; and an environmentally resistant coating disposed on a surface of the niobium-based refractory metal intermetallic composite, the environmentally resistant coating comprising silicon, titanium, chromium, and niobium.
- A second aspect of the invention is to provide an environmentally resistant coating for a niobium-based refractory metal intermetallic composite (Nb-based RMIC) substrate. The environmentally resistant coating comprises between about 43 and 67 atomic percent silicon; between about 2 and about 25 atomic percent titanium; between about 1 and about 25 atomic percent chromium; and a balance of niobium.
- A third aspect of the invention is to provide a turbine system having at least one turbine component. The turbine component comprises: a niobium-based refractory metal intermetallic composite (Nb-based RMIC), said niobium-based refractory metal intermetallic composite comprising titanium, hafnium, silicon, chromium, and a balance of niobium; an environmentally resistant coating disposed on a surface of the niobium-based refractory metal intermetallic composite substrate; and a thermal barrier coating disposed on an outer surface of the environmentally resistant coating. The environmentally resistant coating comprises between about 43 and 67 atomic percent silicon; between about 2 and about 25 atomic percent titanium; between about 1 and about 25 atomic percent chromium; and a balance of niobium.
- A fourth aspect of the invention is to provide a method of making a turbine component comprising a niobium-based refractory metal intermetallic composite (Nb-based RMIC) and having an environmentally resistant coating disposed on the surface of the component, The environmentally resistant coating comprises silicon, titanium, chromium, and niobium. The method comprises the steps of providing a niobium-based refractory metal intermetallic composite substrate formed into the turbine component and depositing the environmentally resistant coating onto the surface of the component.
- Finally, a fifth aspect of the present invention is to provide a method of coating a niobium-based refractory metal intermetallic composite (Nb-based RMIC) substrate with an environmentally resistant coating. The environmentally resistant coating comprises silicon, titanium, chromium, and a balance of niobium. The method comprises the steps of providing a niobium-based refractory metal intermetallic composite substrate and depositing the environmentally resistant coating onto the surface of the niobium-based refractory metal intermetallic composite substrate.
- These and other aspects, advantages, and salient features of the invention will become apparent from the following detailed description, the accompanying drawings, and the appended claims.
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- FIGURE 1 is a schematic representation of a turbine system;
- FIGURE 2 is a schematic cross-sectional view of an environmentally resistant coating of the present invention deposited on a niobium-based refractory metal intermetallic composite substrate;
- FIGURE 3 is a schematic cross-sectional view of a thermal barrier coating and an environmentally resistant coating of the present invention deposited on a niobium-based refractory metal intermetallic composite substrate;
- FIGURE 4 is a scanning electron microscope (SEM) image of a thermal barrier coating and an environmentally resistant coating of the present invention deposited on a Nb-based RMIC substrate; and
- FIGURE 5 is a SEM image of a thermal barrier coating and an environmentally resistant coating of the present invention deposited on a Nb-based RMIC substrate following cyclic oxidation tests to 2500°F for 100 cycles.
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- In the following detailed description, like reference characters designate like or corresponding parts throughout the several views shown in the figures. It is also understood that terms such as "top," "bottom," "outward," "inward," and the like are words of convenience and are not to be construed as limiting terms.
- Referring to the drawings in general and to Figure 1 in particular, it will be understood that the illustrations are for the purpose of describing a preferred embodiment of the invention and are not intended to limit the invention thereto. Figure 1 is a schematic diagram of a
turbine system 10 of the present invention. Theturbine system 10 may either be an aircraft engine; a land-based turbine system, such as those widely used for power generation; or a marine-based turbine. - The
turbine system 10 of the present invention comprises a number ofturbine components 11 that are subject to temperatures of about 2100°F (about 1150°C) or greater during normal operation. Theseturbine components 11 include, but are not limited to: rotatingblades 12,vanes 16,shrouds 18,nozzles 20,combustors 24, and the like.Such turbine components 11 are formed from niobium-based refractory metal intermetallic composites (hereinafter referred to as "Nb-based RMICs") and have service temperatures that are either at the limit of or exceed those of similar components formed from nickel-based superalloys that are currently in use. - In the present invention, the Nb-based RMICs that are used to form the
turbine components 11 of theturbine system 10 comprise titanium, hafnium, silicon, chromium, and niobium. The Nb-based RMICs preferably each comprise between about 19 atomic percent and about 24 atomic percent titanium; between about 1 atomic percent and about 5 atomic percent hafnium; between about 11 and about 22 atomic percent silicon; between about 5 and about 14 atomic percent chromium; and a balance of niobium. More preferably, the Nb-based RMICs each comprise between about 19 and about 24 atomic percent titanium; between about 1 and about 5 atomic percent hafnium; up to about 7 atomic percent tantalum; between about 11 and about 22 atomic percent silicon; up to about 6 atomic percent germanium; up to about 12 atomic percent boron; between about 5 and about 14 atomic percent chromium; up to about 4 atomic percent iron; up to about 4 atomic percent aluminum; up to about 3 atomic percent tin; up to about 3 atomic percent tungsten; up to about 3 atomic percent molybdenum; and a balance of niobium. Most preferably, silicon, germanium, and boron together comprise between about 11 and about 24 atomic percent of the Nb-based RMIC, iron and chromium together comprise between about 5 and about 14 atomic percent of the Nb-based RMIC, and a ratio of a sum of atomic percentages of niobium and tantalum present in the Nb-based RMIC to a sum of atomic percentages of titanium and hafnium in the Nb-based RMIC has a value of between about 1.4 and about 2.2; i.e., 1.4<(Nb+Ta):(Ti+Hf)<2.2. - In the present invention, oxidation of the
turbine components 10 formed from Nb-based RMICs is a concern, as such materials can undergo rapid oxidation at temperatures in the range between about 2000°F and about 2500°F (between about 1090°C and about 1370°C. The slow-growing oxide scale that usually forms on Nb-based RMIC's at these temperatures is typically not a protective oxide scale. In addition, another type of oxidation, known as 'pesting,' occurs at intermediate temperatures (e.g., between about1400°F an about 1800°F). Pesting is a phenomenon that is characterized by the disintegration of a material into pieces or powders after exposure at intermediate temperatures. Refractory metals, particularly molybdenum, exhibit poor resistance to pesting oxidation. - To improve the oxidation and pesting resistance of the
turbine components 11 that are formed from Nb-based RMICs, the present invention includes an environmentallyresistant coating 34 disposed on asurface 33 of the Nb-basedRMIC substrate 32 to form a coated Nb-basedRMIC article 30, such as a coated turbine component, as shown in Figure 2. The environmentallyresistant coating 34 has a thickness of between about 10 microns and about 200 microns and comprises silicon, titanium, chromium, and niobium. It is desirable that the environmentallyresistant coating 34 comprise between about 43 and 67 atomic percent silicon; between about 2 and about 25 atomic percent titanium; between about 1 and about 25 atomic percent chromium; and a balance of niobium. The environmentallyresistant coating 34 may further comprise at least one metal selected from the group consisting of boron, iron, and tin, wherein the total amount of these elements comprises less than about 5 atomic percent of the environmentally resistant coating. In addition, the environmentallyresistant coating 34 may further comprise up to about 20 atomic percent germanium, where germanium replaces silicon. The environmentallyresistant coating 34 may also include up to about 3 atomic percent of at least one element selected from the group consisting of hafnium, tantalum, aluminum, tungsten, and molybdenum. - The environmentally
resistant coating 34 preferably comprises between about 50 and about 67 atomic percent silicon, between about 8 and about 16 atomic percent titanium, between about 4 and about 12 atomic percent chromium, and a balance of niobium. Most preferably, the environmentallyresistant coating 34 comprises about 66 atomic percent silicon, about 10 atomic percent titanium, about 5 atomic percent chromium, and a balance of niobium. - The phase Nb1-x-yTixCrySi2 phase, in which 1 > (x+y) ≥ 0, comprises at least about 50 volume percent of the environmentally resistant coating. The phase Nb1-x-yTixCrySi2 may be concentrated in an
outer region 36 adjacent to theouter surface 40 of the environmentallyresistant coating 34. Other phases, such as a Ti5-zNbzSi4 phase, and a Ti5-wNbwSi3 phase, where 5 > z, w ≥ 0, may also be present in the environmentallyresistant coating 34. These phases may also contain small amounts of chromium and hafnium, and may be concentrated in aninterfacial zone 38 adjacent to theinterface 39 between the environmentallyresistant coating 34 and of the Nb-basedRMIC substrate 32. - The environmentally
resistant coating 34 may be applied to a Nb-basedRMIC substrate 32, such as aturbine component 11, by one of a number of deposition techniques. One such technique is to dip the Nb-basedRMIC substrate 32 into a slurry comprising a viscous binder and containing silicon, chromium, and titanium. After dipping, the Nb-basedRMIC substrate 32 is then heat treated at a temperature of at least about 1200°C, preferably for at least about one hour, to form the environmentallyresistant coating 34. During the heat treatment at 1200°C, the slurry reacts with niobium in the Nb-basedRMIC substrate 32 to form the environmentally resistant layer of the present invention. An additional heat treatment at 1600°C for 10 hours may be used to consolidate the environmentallyresistant coating 34. Other methods, including ion plasma deposition, vacuum plasma spraying, high velocity oxy-flame spraying, physical vapor deposition, chemical vapor deposition, and combinations thereof, can be used to deposit silicon, chromium, titanium, and niobium on the Nb-basedRMIC substrate 32. The environmentallyresistant coating 34 is then formed by heat treating the Nb-basedRMIC substrate 32 at a temperature of at least about 1200°C, preferably for at least about one hour. - Preferably, a
thermal barrier coating 42 may be applied in addition to the environmentallyresistant coating 34 to provide a thermal barrier coated Nb-basedRMIC article 50, such as a coated turbine component, as shown in Figure 3. Thethermal barrier coating 42 is deposited on theouter surface 40 of the environmentallyresistant coating 34. Thethermal barrier coating 42 has a thickness of between about 50 microns and about 400 microns, and may comprise: zirconia; zirconia stabilized by the addition of other metals, such as yttrium, magnesium, cerium, and the like; zircon; mullite; combinations thereof; or other refractory materials having similar properties. - Once the
thermal barrier coating 42 and environmentallyresistant coating 34 have been applied to aturbine component 11, the thermal barrier coatedturbine component 50 may installed in theturbine system 10. - The following example serves to illustrate the features and advantages of the present invention.
- Nb-based RMIC test buttons were coated with the environmentally resistant coating of the present invention. A thermal barrier coating of yttria-stabilized zirconia (YSZ) was deposited on top of the environmentally resistant coating using an air plasma spraying method. A representative microstructure of a
test button 62 coated with the environmentallyresistant coating 34 of the present invention and the YSZthermal barrier coating 42 is shown in Figure 4. The environmentallyresistant coating 34 shown in Figure 4 has a composition of about 66 atomic percent silicon, about 10 atomic percent titanium, about 5 atomic percent chromium, and about 19 atomic percent niobium. The phase Nb1-x-yTixCrySi2 is concentrated in anouter region 36 adjacent to theouter surface 40 of the environmentallyresistant coating 34. - The
interfacial zone 38 of the environmentallyresistant coating 34 adjacent to thesubstrate test button 62 contains a Ti5-xNbxSi4 phase and a Ti5-xNbxSi3 phase. Theinteraction zone 38 has a composition of about 44 atomic percent silicon, about 19 atomic percent titanium, about 5 atomic percent chromium, about 1 atomic percent hafnium, and about 31 atomic percent niobium. Due to the brittle nature of the Nb1-x-yTixCrySi2 phase and the difference in coefficients of thermal expansion (CTE) between the different phases, cracks 54 have formed in the environmentally resistant coating. Thesecracks 54 are self-healing; i.e., they do not propagate further with additional high temperature exposure or thermal cycling. - The Nb-based
RMIC test buttons 62 coated with the environmentallyresistant coating 34 of the present invention and the YSZthermal barrier coating 42 were subjected to furnace cycle tests (FCT) to 1600°F, 2400°F, and 2500°F. During the furnace cycle tests, the coated Nb-based RMIC test buttons were heated to the high temperature for 1 hour in air and then removed from the furnace and cooled for 10 minutes with blowing air. The specimens were then re-loaded into the high temperature furnace. These tests were repeated for 100 times, or cycles, for each test temperature. A post-FCT examination of the coated Nb-based RMIC test buttons was carried out using scanning electron microscopy (SEM). A representative SEM image of a cross section of a coated Nb-based RMIC test button that had been subjected to a furnace cycle test to 2500°F for 100 cycles is shown in Figure 5. As can be seen in Figure 5, thethermal barrier coating 42 and environmentallyresistant coating 34 remained intact and still adhered to the Nb-basedRMIC test button 62 substrate. In a series of furnace cycle tests, no internal oxidation of the Nb-basedRMIC test button 62 substrates was observed during the SEM examination. In addition, no pesting of the Nb-basedRMIC test button 62 substrates was observed at any of the test temperatures. The furnace cycle tests thus show that the susceptibility of Nb-based RMICS to both high temperature oxidation and pesting at intermediate temperatures is significantly reduced by the presence of the environmentally resistant coating of the present invention and a thermal barrier coating. - While various embodiments are described herein, it will be apparent from the specification that various combinations of elements, variations, or improvements therein may be made by those skilled in the art, and are thus within the scope of the invention. For example, the method of depositing the environmentally resistant coating may include any combination of the various methods described herein. In addition, the thermal barrier coating may comprise other refractory materials other than those described herein. Also, it is contemplated that Nb-based RMICs having the environmentally resistant coating may find use other applications in which oxidation resistance at high temperature materials is a desired property.
- For the sake of good order, various features of the invention are set out in the following clauses:-
- 1. A turbine system (10) having at least one turbine component
(11), said turbine component (11) comprising:
- a) at least one niobium-based refractory metal intermetallic composite, said niobium-based refractory metal intermetallic composite comprising titanium, hafnium, silicon, chromium, and niobium; and
- b) an environmentally resistant coating (34)disposed on a surface (33) of said niobium-based refractory metal intermetallic composite, said environmentally resistant coating comprising silicon, titanium, chromium, and niobium.
- 2. The turbine system (10) of Clause 1, wherein said turbine component (11) further comprises a thermal barrier coating (42) disposed on an outer surface of said environmentally resistant coating (34).
- 3. The turbine system (10) of Clause 2, wherein said thermal barrier coating (42) comprises at least one material selected from the group consisting of zirconia, stabilized zirconia, zircon, mullite, and combinations thereof.
- 4. The turbine system (10) of Clause 2, wherein said thermal barrier coating (42) has a thickness of between about 50 microns and about 400 microns.
- 5. The turbine system (10) of Clause 1, wherein said niobium-based refractory metal intermetallic composite comprises: between about 19 atomic percent and about 24 atomic percent titanium; between about 1 atomic percent and about 5 atomic percent hafnium; between about 11 and about 22 atomic percent silicon; between about 5 and about 14 atomic percent chromium; and a balance of niobium.
- 6. The turbine system (10) of Clause 1, wherein said niobium-based refractory metal intermetallic composite comprises: between about 19 and about 24 atomic percent titanium; between about 1 and about 5 atomic percent hafnium; up to about 7 atomic percent tantalum; between about 11 and about 22 atomic percent silicon; up to about 6 atomic percent germanium; up to about 12 atomic percent boron; between about 5 and about 14 atomic percent chromium; up to about 4 atomic percent iron; up to about 4 atomic percent aluminum; up to about 3 atomic percent tin; up to about 3 atomic percent tungsten; up to about 3 atomic percent molybdenum; and a balance of niobium.
- 7. The turbine system (10) of Clause 6, wherein a ratio of a sum of atomic percentages of niobium and tantalum present in said niobium-based refractory metal intermetallic composite to a sum of atomic percentages of titanium and hafnium in said niobium-based refractory metal intermetallic composite has a value between about 1.4 and about 2.2, wherein silicon, germanium, and boron together comprise between about 11 and about 24 atomic percent of said niobium-based refractory metal intermetallic composite, and wherein iron and chromium together comprise between about 5 and about 14 atomic percent of said niobium-based refractory metal intermetallic composite.
- 8. The turbine system (10) of Clause 1, wherein said environmentally resistant coating (34) comprises: between about 43 and 67 atomic percent silicon; between about 2 and about 25 atomic percent titanium; between about 1 and about 25 atomic percent chromium; and a balance of niobium.
- 9. The turbine system (10) of Clause 8, wherein said environmentally resistant coating (34) comprises between about 50 and about 67 atomic percent silicon, between about 8 and about 16 atomic percent titanium, between about 4 and about 12 atomic percent chromium, and a balance of niobium.
- 10. The turbine system (10) of Clause 9, wherein said environmentally resistant coating (34) comprises about 66 atomic percent silicon, about 10 atomic percent titanium, about 5 atomic percent chromium, and a balance of niobium.
- 11. The turbine system (10) of Clause 8, wherein said environmentally resistant coating (34) further comprises at least one element selected from the group consisting of boron, tin, and iron, wherein boron, tin, and iron together comprise up to about 5 atomic percent of said environmentally resistant coating (34).
- 12. The turbine system (10) of Clause 8, wherein said environmentally resistant coating (34) further comprises up to about 20 atomic percent germanium, wherein germanium replaces silicon.
- 13. The turbine system (10) of Clause 8, wherein said environmentally resistant coating (34) further comprises up to about 3 atomic percent of at least one element selected from the group consisting of hafnium, tantalum, aluminum, tungsten, and molybdenum.
- 14. The turbine system (10) of Clause 1, wherein said environmentally resistant coating (34) has a thickness of between about 10 microns and about 200 microns.
- 15. The turbine system (10) of Clause 1, wherein said turbine component (11) is a component selected from the group consisting of rotating blades (12), vanes (16), shrouds (18), nozzles (20), and combustors (24).
- 16. The turbine system (10) of Clause 1, wherein said turbine system (10) is an aircraft turbine system.
- 17. The turbine system (10) of Clause 1, wherein said turbine system (10) is a land-based turbine system.
- 18. The turbine system (10) of Clause 1, wherein said turbine system (10) is a marine turbine system.
- 19. The turbine system (10) of Clause 1, wherein said turbine component (11) is resistant to oxidation in the range from about 2000°F to about 2500°F.
- 20. The turbine system (10) of Clause 1, wherein said turbine component (11) is resistant to pesting in the range from about 1400°F to about 1800°F.
- 21. An environmentally resistant coating (34) for a niobium-based refractory metal intermetallic composite substrate (32), said environmentally resistant coating (34) comprising between about 43 and 67 atomic percent silicon; between about 2 and about 25 atomic percent titanium; between about 1 and about 25 atomic percent chromium; and a balance of niobium.
- 22. The environmentally resistant coating (34) of Clause 21, further comprising a Nb1-x-yTixCrySi2 phase, wherein 1 > (x+y) ≥ 0, and wherein said Nb1-x-yTixCrySi2 phase comprises at least 50 volume percent of said environmentally resistant coating (34).
- 23. The environmentally resistant coating (34) of Clause 22, further comprising at least one phase selected from the group consisting of a Ti5-zNbzSi4 phase, and a Ti5-wNbwSi3 phase, wherein 5 > z, w ≥ 0.
- 24. The environmentally resistant coating (34) of Clause 23, wherein said Nb1-x-yTixCrySi2 phase is concentrated near an outer surface (40) of said environmentally resistant coating (34) and wherein said Ti5-zNbzSi4 phase, and said Ti5-wNbwSi3 phase are concentrated at an interfacial zone (38) between said environmentally resistant coating (34) and said niobium-based refractory metal intermetallic composite substrate (32).
- 25. The environmentally resistant coating (34) of Clause 21, wherein said environmentally resistant coating (34) comprises between about 50 and about 67 atomic percent silicon, between about 8 and about 16 atomic percent titanium, between about 4 and about 12 atomic percent chromium, and a balance of niobium.
- 26. The environmentally resistant coating (34) of Clause 21, wherein said environmentally resistant coating (34) comprises about 66 atomic percent silicon, about 10 atomic percent titanium, about 5 atomic percent chromium, and a balance of niobium.
- 27. The environmentally resistant coating (34) of Clause 21, wherein said environmentally resistant coating (34) further comprises at least one element selected from the group consisting of boron, tin, and iron, wherein boron, tin, and iron together comprise up to about 5 atomic percent of said environmentally resistant coating (34) .
- 28. The environmentally resistant coating (34) of Clause 21, wherein said environmentally resistant coating (34) further comprises up to about 20 atomic percent germanium, wherein germanium replaces silicon.
- 29. The environmentally resistant coating (34) of Clause 21, wherein said environmentally resistant coating (34) further comprises up to about 1 atomic percent of at least one element selected from the group consisting of hafnium, tantalum, aluminum, tungsten, and molybdenum.
- 30. The environmentally resistant coating (34) of Clause 21, wherein said environmentally resistant coating (34) has a thickness of between about 10 microns and about 200 microns.
- 31. The environmentally resistant coating (34) of Clause 21, wherein said niobium-based refractory metal intermetallic composite substrate (32) is a turbine component (11).
- 32. A turbine system (10) having at least one turbine component,
said turbine component comprising:
- a) at least one niobium-based refractory metal intermetallic composite, said niobium-based refractory metal intermetallic composite comprising titanium, hafnium, silicon, chromium, and niobium;
- b) an environmentally resistant coating (34) disposed on a surface of said niobium-based refractory metal intermetallic composite substrate, said environmentally resistant coating (34) comprising between about 43 and 67 atomic percent silicon; between about 2 and about 25 atomic percent titanium; between about 1 and about 25 atomic percent chromium; and a balance of niobium; and
- c) a thermal barrier coating (42) disposed on an outer surface of said environmentally resistant coating (34).
- 33. The turbine system (10) of
Clause 32, wherein said thermal barrier coating comprises at least one material selected from the group consisting of zirconia, stabilized zirconia, zircon, mullite, and combinations thereof. - 34. The turbine system (10) of
Clause 32, wherein said thermal barrier coating (42) has a thickness of between about 50 microns and about 400 microns. - 35. The turbine system (10) of
Clause 32, wherein said niobium-based refractory metal intermetallic composite comprises: between about 19 atomic percent and about 24 atomic percent titanium; between about 1 atomic percent and about 5 atomic percent hafnium; between about 11 and about 22 atomic percent silicon; between about 5 and about 14 atomic percent chromium; and a balance of niobium. - 36. The turbine system (10) of
Clause 32, wherein said niobium-based refractory metal intermetallic composite comprises: between about 19 and about 24 atomic percent titanium; between about 1 and about 5 atomic percent hafnium; up to about 7 atomic percent tantalum; between about 11 and about 22 atomic percent silicon; up to about 6 atomic percent germanium; up to about 12 atomic percent boron; between about 5 and about 14 atomic percent chromium; up to about 4 atomic percent iron; up to about 4 atomic percent aluminum; up to about 3 atomic percent tin; up to about 3 atomic percent tungsten; up to about 3 atomic percent molybdenum; and a balance of niobium. - 37. The turbine system (10) of
Clause 36, wherein a ratio of a sum of atomic percentages of niobium and tantalum present in said niobium-based refractory metal intermetallic composite to a sum of atomic percentages of titanium and hafnium in said niobium-based refractory metal intermetallic composite has a value between about 1.4 and about 2.2, wherein silicon, germanium, and boron together comprise between about 11 and about 24 atomic percent of said niobium-based refractory metal intermetallic composite, and wherein iron and chromium together comprise between about 5 and about 14 atomic percent of said niobium-based refractory metal intermetallic composite. - 38. The turbine system (10) of
Clause 32, wherein a Nb1-x-yTixCrySi2 phase, wherein 1 > (x+y) ≥ 0, comprises at least 50 volume percent phase comprises at least 50 volume percent of said environmentally resistant coating (34). - 39. The turbine system (10) of
Clause 38, wherein said environmentally resistant coating (34) further comprises at least one phase selected from the group consisting of a Ti5-zNbzSi4 phase, and a Ti5-wNbwSi3 phase, wherein 5 > z, w ≥ 0. - 40. The turbine system (10) of
Clause 39, wherein said Nb1-x-yTixCrySi2 phase is concentrated near an outer surface (40) of said environmentally resistant coating (34) and wherein said Ti5-zNbzSi4 phase and said Ti5-wNbwSi3 phase are concentrated at an interfacial zone (38) between said environmentally resistant coating (34) and said niobium-based refractory metal intermetallic composite. - 41. The turbine system (10) of
Clause 32, wherein said environmentally resistant coating (34) comprises between about 50 and about 67 atomic percent silicon, between about 8 and about 16 atomic percent titanium, between about 4 and about 12 atomic percent chromium, and a balance of niobium. - 42. The turbine system (10) of Clause 41, wherein said environmentally resistant coating (34) comprises about 66 atomic percent silicon, about 10 atomic percent titanium, about 5 atomic percent chromium, and a balance of niobium.
- 43. The turbine system (10) of
Clause 32, wherein said environmentally resistant coating (34) further comprises at least one element selected from the group consisting of boron, tin, and iron, wherein boron, tin, and iron together comprise up to about 5 atomic percent of said environmentally resistant coating (34). - 44. The turbine system (10) of
Clause 32, wherein said environmentally resistant coating (34) further comprises up to about 20 atomic percent germanium, wherein germanium replaces silicon. - 45. The turbine system (10) of
Clause 32, wherein said environmentally resistant coating (34) further comprises up to about 3 atomic percent of at least one element selected from the group consisting of hafnium, tantalum, aluminum, tungsten and molybdenum. - 46. The turbine system (10) of
Clause 32, wherein said environmentally resistant coating (34) has a thickness of between about 10 microns and about 200 microns. - 47. The turbine system (10) of
Clause 32, wherein said turbine component (11) is a component selected from the group consisting of rotating blades (12), vanes (16), shrouds (18), nozzles (20), and combustors (24). - 48. The turbine system (10) of
Clause 32, wherein said turbine system (10) is an aircraft turbine system (10). - 49. The turbine system (10) of
Clause 32, wherein said turbine system (10) is a land-based turbine system (10). - 50. The turbine system (10) of
Clause 32, wherein said turbine system (10) is a marine turbine system (10). - 51. The turbine system (10) of
Clause 32, wherein said turbine component (11) is resistant to oxidation in the range from about 2000°F to about 2500°F. - 52. The turbine system (10) of
Clause 32, wherein said turbine component (11) is resistant to pesting in the range from about 1400°F to about 1800°F. - 53. A method of making a turbine component (11) comprising a
niobium-based refractory metal intermetallic composite and having an
environmentally resistant coating (34) disposed on the surface of the turbine
component (11), the environmentally resistant coating (34) comprising silicon,
titanium, chromium, and niobium, the method comprising the steps of:
- a) providing a niobium-based refractory metal intermetallic composite substrate (32) formed into the turbine component (11), and
- b) depositing the environmentally resistant coating (34) onto the surface of the turbine component (11).
- 54. The method of Clause 53, wherein the step of depositing the
environmentally resistant coating (34) comprises:
- a) providing a slurry, the slurry comprising a viscous binder and containing silicon, chromium, and titanium;
- b) dipping the niobium-based refractory metal intermetallic composite substrate (32) into the slurry, whereby the niobium-based refractory metal intermetallic composite substrate (32) is coated by the slurry; and
- c) heat treating the niobium-based refractory metal intermetallic composite substrate (32) for at least about one hour at a temperature of at least about 1200°C.
- 55. The method of Clause 53, wherein the step of depositing the
environmentally resistant coating (34) comprises:
- a) depositing silicon, titanium, chromium, and niobium on the niobium-based refractory metal intermetallic composite substrate (32) using a deposition method selected from the group consisting of ion plasma deposition, vacuum plasma spraying, high velocity oxy-fuel spraying, physical vapor deposition, and chemical vapor deposition; and
- b) heat treating the niobium-based refractory metal intermetallic composite substrate (32) for at least about one hour at a temperature of at least about 1200°C.
- 56. The method of Clause 53, further comprising the step of depositing a thermal barrier coating (42) over the environmentally resistant coating (34).
- 57. The method of Clause 53, wherein the environmentally resistant coating (34) comprises between about 43 and 67 atomic percent silicon, between about 2 and about 25 atomic percent titanium, between about 1 and about 25 atomic percent chromium, and a balance of niobium.
- 58. A method of coating a niobium-based refractory metal
intermetallic substrate (32) with an environmentally resistant coating (34), the
environmentally resistant coating (34) comprising silicon, titanium, chromium,
and niobium, the method comprising the steps of:
- a) providing a niobium-based refractory metal intermetallic composite substrate (32); and
- b) depositing the environmentally resistant coating (34) onto the surface of the niobium-based refractory metal intermetallic composite substrate (32).
- 59. The method of Clause 58, wherein the step of depositing the
environmentally resistant coating (34) comprises:
- a) providing a slurry, the slurry comprising a viscous binder and containing silicon, chromium, and titanium;
- b) dipping the niobium-based refractory metal intermetallic composite substrate (32) into the slurry, whereby the niobium-based refractory metal intermetallic composite substrate (32) is coated by the slurry; and
- d) heat treating the niobium-based refractory metal intermetallic composite substrate (32) for at least about one hour at a temperature of at least about 1200°C.
- 60. The method of Clause 58, wherein the step of depositing the
environmentally resistant coating (34) comprises:
- a) depositing silicon, titanium, chromium, and niobium on the niobium-based refractory metal intermetallic composite substrate using a deposition method selected from the group consisting of ion plasma deposition, vacuum plasma spraying, high velocity oxy-fuel spraying, physical vapor deposition, and chemical vapor deposition; and
- b) heat treating the niobium-based refractory metal intermetallic composite substrate (32) for at least about one hour at a temperature of at least about 1200°C.
- 61. The method of Clause 57, wherein the environmentally resistant coating (34) comprises between about 43 and 67 atomic percent silicon, between about 2 and about 25 atomic percent titanium, between about 1 and about 25 atomic percent chromium, and a balance of niobium.
-
Claims (10)
- A turbine system (10) having at least one turbine component (11), said turbine component (11) comprising:a) at least one niobium-based refractory metal intermetallic composite, said niobium-based refractory metal intermetallic composite comprising titanium, hafnium, silicon, chromium, and niobium; andb) an environmentally resistant coating (34)disposed on a surface (33) of said niobium-based refractory metal intermetallic composite, said environmentally resistant coating comprising silicon, titanium, chromium, and niobium.
- The turbine system (10) of Claim 1, wherein said turbine component (11) further comprises a thermal barrier coating (42) disposed on an outer surface of said environmentally resistant coating (34).
- An environmentally resistant coating (34) for a niobium-based refractory metal intermetallic composite substrate (32), said environmentally resistant coating (34) comprising between about 43 and 67 atomic percent silicon; between about 2 and about 25 atomic percent titanium; between about 1 and about 25 atomic percent chromium; and a balance of niobium.
- The environmentally resistant coating (34) of Claim 3, further comprising a Nb1-x-yTixCrySi2 phase, wherein 1 > (x+y) ≥ 0, and wherein said Nb1-x-yTixCrySi2 phase comprises at least 50 volume percent of said environmentally resistant coating (34).
- A turbine system (10) having at least one turbine component, said turbine component comprising:a) at least one niobium-based refractory metal intermetallic composite, said niobium-based refractory metal intermetallic composite comprising titanium, hafnium, silicon, chromium, and niobium;b) an environmentally resistant coating (34) disposed on a surface of said niobium-based refractory metal intermetallic composite substrate, said environmentally resistant coating (34) comprising between about 43 and 67 atomic percent silicon; between about 2 and about 25 atomic percent titanium; between about 1 and about 25 atomic percent chromium; and a balance of niobium; andc) a thermal barrier coating (42) disposed on an outer surface of said environmentally resistant coating (34).
- The turbine system (10) of Claim 5, wherein said thermal barrier coating comprises at least one material selected from the group consisting of zirconia, stabilized zirconia, zircon, mullite, and combinations thereof.
- A method of making a turbine component (11) comprising a niobium-based refractory metal intermetallic composite and having an environmentally resistant coating (34) disposed on the surface of the turbine component (11), the environmentally resistant coating (34) comprising silicon, titanium, chromium, and niobium, the method comprising the steps of:a) providing a niobium-based refractory metal intermetallic composite substrate (32) formed into the turbine component (11), andb) depositing the environmentally resistant coating (34) onto the surface of the turbine component (11).
- A method of coating a niobium-based refractory metal intermetallic substrate (32) with an environmentally resistant coating (34), the environmentally resistant coating (34) comprising silicon, titanium, chromium, and niobium, the method comprising the steps of:a) providing a niobium-based refractory metal intermetallic composite substrate (32); andb) depositing the environmentally resistant coating (34) onto the surface of the niobium-based refractory metal intermetallic composite substrate (32).
- The method of Claim 7 or Claim 8, wherein the step of depositing the environmentally resistant coating (34) comprises:a) providing a slurry, the slurry comprising a viscous binder and containing silicon, chromium, and titanium;b) dipping the niobium-based refractory metal intermetallic composite substrate (32) into the slurry, whereby the niobium-based refractory metal intermetallic composite substrate (32) is coated by the slurry; andc) heat treating the niobium-based refractory metal intermetallic composite substrate (32) for at least about one hour at a temperature of at least about 1200°C, or comprisesa) depositing silicon, titanium, chromium, and niobium on the niobium-based refractory metal intermetallic composite substrate (32) using a deposition method selected from the group consisting of ion plasma deposition, vacuum plasma spraying, high velocity oxy-fuel spraying, physical vapor deposition, and chemical vapor deposition; andb) heat treating the niobium-based refractory metal intermetallic composite substrate (32) for at least about one hour at a temperature of at least about 1200°C.
- The method of Claim 7 or Claim 8, wherein the environmentally resistant coating (34) comprises between about 43 and 67 atomic percent silicon, between about 2 and about 25 atomic percent titanium, between about 1 and about 25 atomic percent chromium, and a balance of niobium.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US775737 | 1996-12-31 | ||
US09/775,737 US6521356B2 (en) | 2001-02-02 | 2001-02-02 | Oxidation resistant coatings for niobium-based silicide composites |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1229146A2 true EP1229146A2 (en) | 2002-08-07 |
EP1229146A3 EP1229146A3 (en) | 2004-03-31 |
Family
ID=25105336
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Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02250499A Withdrawn EP1229146A3 (en) | 2001-02-02 | 2002-01-24 | Oxidation resistant coatings for niobium-based silicide composites |
Country Status (3)
Country | Link |
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US (2) | US6521356B2 (en) |
EP (1) | EP1229146A3 (en) |
JP (1) | JP2002327284A (en) |
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Also Published As
Publication number | Publication date |
---|---|
US20020192491A1 (en) | 2002-12-19 |
EP1229146A3 (en) | 2004-03-31 |
US6645560B2 (en) | 2003-11-11 |
JP2002327284A (en) | 2002-11-15 |
US6521356B2 (en) | 2003-02-18 |
US20030124342A1 (en) | 2003-07-03 |
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